The Transpiration-Cooled Gas Turbine
The Transpiration-Cooled Gas Turbine
复制标题
蒸腾冷却燃气轮机
DOI：
--
复制
发表时间：
1970
期刊：
影响因子：
--
通讯作者：
A. Turner
中科院分区：
文献类型：
--
作者：
F. Bayley;A. Turner
本文介绍了一种用于评价高温燃气轮机蒸腾冷却多孔表面气动和热力学性能的实验和分析研究方案。通过一组喷嘴叶片排出冷却剂的空气动力学损失很小，特别是与所获得的有效冷却所产生的热力学优势相比。虽然射流冷却剂在某些情况下可以通过破坏层流边界层的稳定来增加气体到叶片的传热速率，但在涡轮实践中占主导地位的湍流边界层中，传热不可避免地会减少，这在理论上是可以令人满意地预测的。在燃气轮机的燃烧系统中，蒸腾冷却似乎也很有吸引力，但在火焰管的传热率方面仍有许多工作要做。
This paper describes a program of experimental and analytical research designed to evaluate the aerodynamic and thermodynamic performance of transpiration-cooled porous surfaces in the high-temperature gas turbine. The aerodynamic penalties of effusing coolant through a set of nozzle blades are shown to be small, particularly when compared with the thermodynamic advantages which accrue from the effective cooling obtained. Although the effusing coolant can in certain circumstances increase gas to blade heat transfer rates by destabilizing a laminar boundary layer, in the turbulent boundary layers which predominate in turbine practice there is inevitably a reduction in heat transfer which can be satisfactorily predicted theoretically. In the combustion system of the gas turbine, transpiration cooling appears also to be very attractive, but much work remains to be done on heat transfer rates in the flame-tube.